EP3179077A1 - Kraftstoffregelsystem für gasturbinenmotor eines flugzeugs - Google Patents

Kraftstoffregelsystem für gasturbinenmotor eines flugzeugs Download PDF

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Publication number
EP3179077A1
EP3179077A1 EP15382618.5A EP15382618A EP3179077A1 EP 3179077 A1 EP3179077 A1 EP 3179077A1 EP 15382618 A EP15382618 A EP 15382618A EP 3179077 A1 EP3179077 A1 EP 3179077A1
Authority
EP
European Patent Office
Prior art keywords
fuel
pump
control system
pressure
engine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP15382618.5A
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English (en)
French (fr)
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EP3179077B1 (de
Inventor
Salvatore DEMELAS
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations SL
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Airbus Operations SL
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations SL filed Critical Airbus Operations SL
Priority to EP15382618.5A priority Critical patent/EP3179077B1/de
Priority to ES15382618T priority patent/ES2698380T3/es
Priority to US15/372,645 priority patent/US20170167391A1/en
Publication of EP3179077A1 publication Critical patent/EP3179077A1/de
Application granted granted Critical
Publication of EP3179077B1 publication Critical patent/EP3179077B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/232—Fuel valves; Draining valves or systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/30—Control of fuel supply characterised by variable fuel pump output
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/50—Application for auxiliary power units (APU's)
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/301—Pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/301—Pressure
    • F05D2270/3013—Outlet pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/303—Temperature
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/306—Mass flow
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention refers to a new fuel control, pressurization and dispensing system for a gas turbine engine of an aircraft, in particular, for those aircrafts whose auxiliary power unit and/or main engine fuel control systems comprise a mechanical fuel control unit (FCU), a fuel controller (such as an Engine Electronic Unit (ECU)), and a plurality of nozzles for dispensing the pressurized fuel received from the FCU into the engine combustion chamber.
  • FCU mechanical fuel control unit
  • ECU Engine Electronic Unit
  • An object of the invention is to provide a fuel control system that improves the performance and emission of conventional gas turbine engines, by decoupling the efficiency of the fuel pressurization and delivery into the combustion chamber from the operating phase (start, cooldown, idle, working,.. ) and load condition (step load, full load, partial load, ).
  • Another object of the present invention is to provide a fuel control system that minimizes the weight of conventional fuel control systems, at the same time that simplifies the system, and avoids using the mechanical fuel control unit, allowing saving costs and space when installed in the aircraft.
  • the auxiliary power unit is a gas turbine engine that supplies electrical and pneumatic power to the aircraft systems as an auxiliary or secondary source of power.
  • the APU allows the aircraft to be autonomous of external electric and pneumatic power sources on ground and in-flight.
  • the APU fuel control system is mainly a mechanical system where the fuel controller controls the engine by modulating the fuel pressure delivered to the nozzles from the fuel control unit.
  • a conventional fuel control system comprises a fuel tank (3) containing fuel, a FCU (4), an APU DC fuel pump (8) for feeding the FCU (4) from the fuel tank (3) when main engine fuel pumps are off, an APU gearbox (2) tor mechanically drive the FCU (4), at least one nozzle (10) for dispensing the pressurize fuel received from the FCU (4) into the APU combustion chamber (6), and said APU combustion chamber (6).
  • conventional systems comprise a fuel controller (5) adapted to modulate the fuel pressure delivered to the nozzles (10) by actuating on the FCU (4).
  • Figure 2 shows a conventional nozzle (10) dispensing fuel at different pressures.
  • the nozzle (10) is supplied with a low pressure of fuel.
  • the nozzle (10) is supplied with a medium pressure of fuel.
  • the nozzle (10) is supplied with a high pressure of fuel.
  • the atomization pattern is extended covering great areas and dispensing droplets of minimum size.
  • the present invention overcomes the above mentioned drawbacks by providing a fuel control system that improves the performance and emission of a gas turbine engine, at the same time that provides a simplified system with respect to conventional systems, and achieves a weight and cost reduction.
  • the invention refers to a fuel control system for a gas turbine engine of an aircraft that comprises an engine having a gearbox and a combustion chamber, and a fuel tank for containing fuel.
  • the system further comprises a high pressure fuel pump to pump fuel from the fuel tank towards the combustion chamber, at least one electrically controlled fuel injector to inject a flow rate of the pumped fuel into the combustion chamber, a fuel pressure sensor placed to sense the pressure of the pumped fuel, a fuel temperature sensor placed to sense the temperature of the pumped fuel, and a fuel controller electrically coupled with the fuel pressure and temperature sensors to calculate the fuel density according to the sensed values.
  • the fuel controller is electrically coupled with the at least one fuel injector to determine the fuel flow injection rate.
  • the fuel controller is adapted to calculate the quantity of the injected fuel, according to the fuel density and the fuel flow injection rate. Further, the fuel controller is electrically coupled with the fuel pump to establish a pump output pressure value, according to the quantity of the injected fuel , such that a constant fuel pressure value is supplied to the at least one fuel injector, in order to inject a constant fuel injection pressure in the combustion chamber.
  • the fuel controller is coupled with both the fuel pressure sensor and the fuel temperature sensor to calculate the pumped fuel density, and with the at least one fuel injector to measure the rate of injection that is being delivered by said injector. Based on the fuel density and on the flow injection rate, the fuel controller is capable of calculating the quantity of fuel that is being directly injected in the combustion chamber. According to this, the fuel controller is further adapted to establish an output pressure value on the fuel pump, such that a constant fuel pressure value is supplied to the at least one fuel injector. Thus, a constant fuel injection pressure is injected into the combustion chamber. This way, the required fuel injection rate is reliably injected at any time in the combustion chamber by the at least one fuel injector.
  • the invention achieves that the at least one fuel injector constantly works at a maximum fuel pressure, so that an optimum fuel atomization in all engine operating conditions (speed/load) is ensured.
  • This upgrade in the fuel atomization improves the overall performance of the gas turbine engine.
  • the invention avoids the need of the FCU.
  • the invention Since the FCU is a highly complex and heavy mechanical element that is mechanically driven by the gearbox, the invention confers the system with a weight and simplicity improvement, and also with a better response of the engine at any speed or load condition. Additionally, the invention decouples the fuel atomization from the engine operation.
  • the invention allows removing the DC powered fuel pump, which conventionally feeds the FCU from the fuel tanks when the fuel pumps of the main engines are off.
  • the invention simplifies the fuel control system, and allows reducing installation, recurrent, and direct costs of the mentioned components, and also of those other components required for their functioning. Thus, the invention reduces also the maintenance costs involved by conventional systems.
  • the invention achieves a significant weight reduction by dispensing with the FCU and the DC powered fuel pump, and, in turned only requiring a simple high pressure fuel pump.
  • the invention enables saving space, thereby offering extra room for either harness routing for any other new or existing aircraft system, or placing any new or existing aircraft equipment's.
  • FIG. 3 shows a schematic view of a fuel control system 1 for a gas turbine engine of an aircraft according to the invention.
  • the fuel control system 1 of Figure 3 comprises an engine 18 having a gearbox 2 and a combustion chamber 6, and a fuel tank 3 for containing fuel.
  • the system 1 further comprises a high pressure fuel pump 9, at least one electrically controlled fuel injector 7, a fuel pressure sensor 11, a fuel temperature sensor 12, and a fuel controller 5.
  • the high pressure fuel pump 9 is connected to the fuel tank 3 for pumping fuel from the tank 3 towards the combustion chamber 6.
  • the at least one electrically controlled fuel injector 7 receives the pumped fuel from the fuel pump 9, and is suitable to inject a controllable flow rate of fuel into the combustion chamber 6.
  • the fuel pressure sensor 11 and the fuel temperature sensor 12 are placed to respectively sense the pressure and temperature of the pumped fuel.
  • the fuel controller 5 is electrically coupled with the fuel pump 9, the fuel pressure sensor 11, the fuel temperature sensor 12, and the at least one fuel injector 7.
  • the fuel controller 5 is adapted to calculate the fuel density according to the sensed pressure and temperature values, and to determine the fuel flow injection rate by its coupling with the at least one fuel injector 7. From both parameters, the fuel density and the fuel flow injection rate, the fuel controller 5 is adapted to calculate the quantity of injected fuel to establish a pump output pressure value such that a constant fuel pressure value is supplied to the at least one fuel injector 7.
  • a constant fuel injection pressure is injected in the combustion chamber 6 by the at least one fuel injector 7.
  • the fuel control system 1 achieves supplying a high constant fuel pressure to the at least one fuel injector 7, and thereby, dispensing a constant high fuel injection pressure into the combustion chamber 6.
  • the fuel controller 5 is further adapted to regulate the fuel flow injection rate of the at least one fuel injector 7 for supplying the at least one fuel injector 7 with a high constant fuel pressure value. By regulating the fuel flow injection rate, the fuel controller 5 regulates the quantity of injected fuel.
  • the fuel controller 5 is adapted to control both the output pressure of the pumped fuel 9, and the fuel flow of the at least one fuel injector 7, for supplying the at least one fuel injector 7 with a high constant fuel pressure value.
  • the fuel flow rate of the fuel injector 7 can be varied by the fuel controller 5 for obtaining the desired instantaneous fuel quantity while ensuring a constant input pressure value with which supplying the at least one fuel injector 7.
  • the engine 18 further comprises a shaft and the fuel control system 1 further comprises an engine speed sensor 14, wherein the engine speed sensor 14 is coupled to the engine 18 to sense the instantaneous shaft speed value , and wherein the fuel controller 5 is further adapted to receive instantaneous engine load information 13 and to modify the fuel pump output pressure value considering load and speed values for supplying a constant fuel pressure value to the at least one fuel injector 7.
  • the engine load information 13 can be estimated based on the fuel needed to keep the required engine speed at a given electrical and pneumatic load.
  • This engine load information 13 can be provided by external signals, such as the air flow demand for the engine, or the thrust demand for the main engines.
  • the fuel controller 5 is adapted to modify both the output pressure of the fuel pump 9 and the fuel flow rate of the at least one fuel injector 7, considering the load and speed values of the gas turbine engine in addition to the density and the flow injection rate of the pumped fuel.
  • the fuel controller 5 is further adapted to modify the duty cycle of the fuel pump 9 according to the load and speed values for that a constant fuel pressure value is supplied to the at least one fuel injector 7.
  • the invention allows reducing the power consumption of the fuel pump, passing from a fuel pump in continuous maximum pressure operation, to a fuel pump with lower pressure operation.
  • the fuel pump 9 comprises input valves for receiving fuel to be pumped, and the fuel controller 5 is further adapted to reduce the pump input fuel flow through at least one of said fuel pump input valves, according to the load and/or speed values. This way, the invention further optimizes the high pressure pump power consumption.
  • the fuel control system 1 further comprises an input airflow pressure 15 and air temperature sensor 16, both located in an engine air inlet, to respectively sense pressure and temperature values of the input airflow, and wherein the fuel controller 5 is further adapted to modify the fuel pump output pressure value considering the inlet airflow pressure and/or temperature values, for supplying a constant fuel pressure value to the at least one fuel injector 7.
  • the fuel controller 5 is adapted to modify both the output pressure of the fuel pump 9 and the fuel flow rate of the at least one fuel injector 7, considering the monitored engine air inlet pressure and temperature values to optimize the fuel injection flow rate taking into account the computed air density in addition to the load and speed values.
  • the fuel control system 1 comprises a plurality of fuel injectors 7, and the fuel controller 5 is adapted to individually control the fuel flow rate of each one of the injectors 7.
  • the fuel pressure sensor 11 and the fuel temperature sensor 12 are coupled to a pipeline 17 that connects the fuel pump 9 with the at least one fuel injector 7.
  • the fuel pressure sensor 11 and the fuel temperature sensor 12 are coupled to an output of the fuel pump 9.
  • the fuel pump 9 is a mechanical pump, which is mechanically driven by the gearbox 2.
  • the fuel pump 9 is an electrical pump.
  • the fuel pump 9 can be decoupled from the gearbox 2 and can be located close to the fuel tanks.
  • the electrically powered fuel pump allows better control of the delivered fuel pressure, since it has no relation with the engine speed. Also, the electrical pump helps to save energy in case of low fuel demand.
  • the fuel control system 1 further comprises a linear motor, and the fuel pump 9 is driven by said linear motor.
  • a linear motor has a single friction point, involving fewer losses, less acoustic noise, and greater reliability.
  • the at least one fuel pump 9 is integrated into each injector 7 of the at least one fuel injector 7 to form a pump-injector element.
  • the pumping element can also be driven by a linear motor.
  • the gas turbine engine consists of an auxiliary power unit.
  • the invention further comprises an aircraft comprising the fuel control system 1 as described.
  • the fuel control system of the invention presents the following advantages:
  • Figure 5 shows the droplet size obtained by conventional nozzles.
  • the horizontal axis is a logarithmic scale of particle size x in ⁇ m.
  • the vertical axis on the right side is a linear scale of distribution density Q31g(x) as a function of the particle size x.
  • Figure 6 shows a typical droplet pattern of a high pressure injection by the at least one electrically controlled fuel injector.
  • the droplet size of the fuel injectors of Figure 6 is almost an order of magnitude lower than the size obtainable with the traditional nozzles of Figure 5 .

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Electrical Control Of Air Or Fuel Supplied To Internal-Combustion Engine (AREA)
EP15382618.5A 2015-12-11 2015-12-11 Kraftstoffregelsystem für gasturbinenmotor eines flugzeugs Not-in-force EP3179077B1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP15382618.5A EP3179077B1 (de) 2015-12-11 2015-12-11 Kraftstoffregelsystem für gasturbinenmotor eines flugzeugs
ES15382618T ES2698380T3 (es) 2015-12-11 2015-12-11 Sistema de control de combustible para un motor de turbina de gas de una aeronave
US15/372,645 US20170167391A1 (en) 2015-12-11 2016-12-08 Fuel Control System For A Gas Turbine Engine Of An Aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15382618.5A EP3179077B1 (de) 2015-12-11 2015-12-11 Kraftstoffregelsystem für gasturbinenmotor eines flugzeugs

Publications (2)

Publication Number Publication Date
EP3179077A1 true EP3179077A1 (de) 2017-06-14
EP3179077B1 EP3179077B1 (de) 2018-09-12

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP15382618.5A Not-in-force EP3179077B1 (de) 2015-12-11 2015-12-11 Kraftstoffregelsystem für gasturbinenmotor eines flugzeugs

Country Status (3)

Country Link
US (1) US20170167391A1 (de)
EP (1) EP3179077B1 (de)
ES (1) ES2698380T3 (de)

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KR20200094666A (ko) * 2019-01-29 2020-08-07 더 보잉 컴파니 속도 보상을 갖춘 항공기 보조 동력 장치(apu) 제어 시스템
US11034463B2 (en) 2019-03-26 2021-06-15 The Boeing Company Aircraft auxiliary power unit (APU) control system having variably sized air inlet
RU2753207C1 (ru) * 2020-10-14 2021-08-12 Федеральное Автономное Учреждение "Центральный институт авиационного моторостроения имени П.И. Баранова" Система подачи топлива в многоколлекторную камеру сгорания
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CN115492687B (zh) * 2021-06-17 2025-11-04 通用电气公司 管理热燃料的控制方法
US11821366B2 (en) 2021-06-17 2023-11-21 General Electric Company Methods of control for management of hot fuel
US12031492B2 (en) 2021-10-12 2024-07-09 Hamilton Sundstrand Corporation Electric fuel control closed loop aircraft fuel system
GB202201313D0 (en) 2022-02-02 2022-03-16 Rolls Royce Plc Combination of a gas turbine engine and a power electronics
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GB2578106A (en) * 2018-10-15 2020-04-22 Eaton Intelligent Power Ltd Variable demand fuel pump
US10974844B2 (en) 2019-01-29 2021-04-13 The Boeing Company Aircraft auxiliary power unit (APU) control system having speed compensation
KR20200094666A (ko) * 2019-01-29 2020-08-07 더 보잉 컴파니 속도 보상을 갖춘 항공기 보조 동력 장치(apu) 제어 시스템
KR20200094665A (ko) * 2019-01-29 2020-08-07 더 보잉 컴파니 속도 보상을 갖춘 항공기 보조 동력 장치(apu) 제어 시스템
JP2020125105A (ja) * 2019-01-29 2020-08-20 ザ・ボーイング・カンパニーＴｈｅ Ｂｏｅｉｎｇ Ｃｏｍｐａｎｙ 速度補償機能を有する航空機用補助動力装置（ａｐｕ）制御システム
JP2020125104A (ja) * 2019-01-29 2020-08-20 ザ・ボーイング・カンパニーＴｈｅ Ｂｏｅｉｎｇ Ｃｏｍｐａｎｙ 速度補償機能を有する航空機用補助動力装置（ａｐｕ）制御システム
EP3690216A1 (de) * 2019-01-29 2020-08-05 The Boeing Company Flugzeughilfstriebwerk mit geschwindigkeitskompensation
US10988266B2 (en) 2019-01-29 2021-04-27 The Boeing Company Aircraft auxiliary power unit (APU) control system having speed compensation
KR102692770B1 (ko) 2019-01-29 2024-08-06 더 보잉 컴파니 속도 보상을 갖춘 항공기 보조 동력 장치(apu) 제어 시스템
US11034463B2 (en) 2019-03-26 2021-06-15 The Boeing Company Aircraft auxiliary power unit (APU) control system having variably sized air inlet
RU2753207C1 (ru) * 2020-10-14 2021-08-12 Федеральное Автономное Учреждение "Центральный институт авиационного моторостроения имени П.И. Баранова" Система подачи топлива в многоколлекторную камеру сгорания
CN114718737A (zh) * 2022-04-11 2022-07-08 中国航发控制系统研究所 一种电动燃油泵的流量开环控制方法
CN114718737B (zh) * 2022-04-11 2023-09-05 中国航发控制系统研究所 一种电动燃油泵的流量开环控制方法

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